CN114491842A - Unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium - Google Patents
Unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium Download PDFInfo
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Abstract
The application discloses unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium, through carrying out loading space adjustment, weight focus matching, adopting design such as universalization interface, change quick-witted upper system to unmanned aerial vehicle, can load the guided weapon of multiple different models in proper order in same operation position of same unmanned aerial vehicle platform, and efficiency is higher in the actual combat experiment.
Description
Technical Field
The application relates to the field of unmanned aerial vehicle guided weapon design, in particular to an unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium.
Background
The guided weapon is a general name of various weapons which control the flying direction, attitude, height and speed of the weapon according to a certain rule and guide the warhead to accurately attack the target, usually, the guided weapon is designed and manufactured by different manufacturers, and the parameters of each guided weapon are different.
In the actual combat experiment, a certain type of guided weapon is usually installed on a suitable unmanned aerial vehicle platform, a plurality of unmanned aerial vehicles load a plurality of guided weapons, or the guided weapons are laid on the ground, and then follow-up experiments are carried out in sequence, so that the efficiency of the existing assembly mode is low.
Disclosure of Invention
The application mainly aims to provide an unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium, and aims to solve the technical problem that assembly mode efficiency is low in actual combat experiments.
In order to achieve the purpose, the application provides an unmanned aerial vehicle guided weapon interchange design method, which comprises the following steps:
acquiring the body parameters of a target unmanned aerial vehicle and the weapon parameters of a pre-equipped guidance weapon group; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons;
according to the size relation between the maximum weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle, adjusting the loading space of the target unmanned aerial vehicle so as to enable the guided weapon to have a safe movement distance with the body shape of the target unmanned aerial vehicle when in operation;
adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, wherein the mechanical interface is matched with the guided weapons of the plurality of models;
according to the number and the type of the communication interfaces of the guided weapon group, a standard communication interface is installed on the target unmanned aerial vehicle;
and changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guided weapon group.
Optionally, the step of adjusting the loading space of the target drone according to the size relationship between the size of the largest weapon in the guided weapon group and the size of the load compartment of the target drone, so that the guided weapon runs at a safe movement distance from the body shape of the target drone, includes:
judging whether the maximum weapon size in the guided weapon group is larger than the load cabin size of the target unmanned aerial vehicle or not;
if yes, a partition plate is arranged in a front landing gear cabin of the target unmanned aerial vehicle.
Optionally, the step of adjusting the center of gravity of the target drone according to the weight of each guided weapon in the guided weapon group so that the center of gravity of the target drone does not exceed the fluctuation range of the center of gravity of the target drone includes:
adjusting the center of gravity of the target unmanned aerial vehicle by adjusting the position and/or the counterweight of the airborne equipment of the target unmanned aerial vehicle.
Optionally, the step of installing a mechanical interface on the target drone according to the installation angle of each guided weapon in the guided weapon group, where the mechanical interface matches the plurality of models of guided weapons includes:
the mechanical interface is a metal support which can stretch out and draw back in length, zoom in and zoom out in diameter and rotate in angle according to the installation angles of different guided weapons.
Optionally, the power supply mode of the guided weapon group comprises a plurality of direct current power supply modes;
the step of changing the target unmanned aerial vehicle electrical system according to the power consumption requirement of the guided weapon group comprises:
and according to the direct current power supply mode of the guided weapon group, setting different direct current power supply devices and direct current conversion units on the target unmanned aerial vehicle.
Optionally, the step of modifying the target drone electrical system according to the power demand of the guided weapon group includes:
through reducing target unmanned aerial vehicle's power consumption, satisfy the maximum power consumption demand of guide wu jia group.
Optionally, the step of modifying the target drone electrical system according to the power demand of the guided weapon group includes:
and meeting the single limit power utilization requirement of the guided weapon by overloading the engine of the target unmanned aerial vehicle and limiting the single power utilization time.
In addition, for realizing above-mentioned purpose, this application still provides an unmanned aerial vehicle guided weapon exchanges design device, includes:
the data acquisition module is used for acquiring the body parameters of the target unmanned aerial vehicle and the weapon parameters of the pre-equipped guided weapon group; the fuselage parameters comprise load compartment size, gravity fluctuation range, guided munition operation position and power supply capacity, the munition parameters comprise munition size, total weight, installation angle, number of communication interfaces, type of communication interfaces and power demand, and the guided munition group comprises a plurality of types of guided munitions;
the loading space adjusting module is used for adjusting the loading space of the target unmanned aerial vehicle according to the size relation between the size of the largest weapon in the guided weapon group and the size of a load cabin of the target unmanned aerial vehicle, so that a safe movement distance is reserved between the guided weapon and the body shape of the target unmanned aerial vehicle when the guided weapon operates;
the gravity center adjusting module is used for adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
the mechanical interface installation module is used for installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, and the mechanical interface is matched with the guided weapons of the plurality of models;
the communication interface installation module is used for installing a standardized communication interface on the target unmanned aerial vehicle according to the number and the type of the communication interfaces of the guided weapon group;
and the electrical system changing module is used for changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guidance weapon group.
In addition, to achieve the above object, the present application further provides a production apparatus, which includes a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the above method.
In addition, to achieve the above object, the present application further provides a computer readable storage medium, where a computer program is stored, and a processor executes the computer program to implement the above method.
The beneficial effect that this application can realize.
According to the unmanned aerial vehicle guided weapon interchange design method, the unmanned aerial vehicle guided weapon interchange design device, the unmanned aerial vehicle guided weapon interchange design equipment and the storage medium, the fuselage parameters of a target unmanned aerial vehicle and the weapon parameters of a pre-equipped guided weapon group are obtained; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons; according to the size relation between the maximum weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle, adjusting the loading space of the target unmanned aerial vehicle so as to enable the guided weapon to have a safe movement distance with the body shape of the target unmanned aerial vehicle when in operation; adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle; installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, wherein the mechanical interface is matched with the guided weapons of the plurality of models; according to the number and the type of the communication interfaces of the guided weapon group, a standard communication interface is installed on the target unmanned aerial vehicle; and changing the target unmanned aerial vehicle electrical system according to the power consumption requirement of the guided weapon group. The unmanned aerial vehicle is subjected to loading space adjustment, weight gravity center matching, universal interface adoption, change of onboard system and other designs, various types of guided weapons can be loaded in sequence at the same operation position of the same unmanned aerial vehicle platform, and the efficiency is higher in actual combat experiments.
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FIG. 1 is a schematic diagram of a production facility in a hardware operating environment according to an embodiment of the present disclosure;
fig. 2 is a schematic flowchart of a method for designing guided weapon interchange of an unmanned aerial vehicle according to an embodiment of the present application;
fig. 3 is a functional module schematic diagram of an unmanned aerial vehicle guided weapon interchange design device provided in an embodiment of the present application;
fig. 4 is a schematic view of a gravity center fluctuation range of the unmanned aerial vehicle provided by the embodiment of the present application.
The implementation, functional features and advantages of the objectives of the present application will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The main solution of the embodiment of the application is as follows: according to the provided unmanned aerial vehicle guided weapon interchange design method, device, equipment and storage medium, the fuselage parameters of a target unmanned aerial vehicle and the weapon parameters of a pre-equipped guided weapon group are obtained; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons; according to the size relation between the maximum weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle, adjusting the loading space of the target unmanned aerial vehicle so as to enable the guided weapon to have a safe movement distance with the body shape of the target unmanned aerial vehicle when in operation; adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle; installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, wherein the mechanical interface is matched with the guided weapons of the plurality of models; according to the number and the type of the communication interfaces of the guided weapon group, a standard communication interface is installed on the target unmanned aerial vehicle; and changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guided weapon group.
The guided weapon is a general name of various weapons which control the flying direction, attitude, height and speed of the weapon according to a certain rule and guide the warhead to accurately attack the target, usually, the guided weapon is designed and manufactured by different manufacturers, and the parameters of each guided weapon are different.
In the actual combat test, a certain type of guided weapon is usually installed on a suitable unmanned aerial vehicle platform, a plurality of unmanned aerial vehicles simultaneously load the guided weapon, or the guided weapons are placed on the ground, and then follow-up tests are sequentially carried out, so that the efficiency of the existing assembly mode is low.
Therefore, the application provides a solution, through carrying out loading space adjustment, weight focus to unmanned aerial vehicle and matching, take universalization interface, change design such as quick-witted upper system, can load the guidance weapon of multiple different models in proper order in the same operation position of same unmanned aerial vehicle platform, and efficiency is higher in the actual combat experiment.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a production device in a hardware operating environment according to an embodiment of the present application.
As shown in fig. 1, the production apparatus may include: a processor 1001, such as a Central Processing Unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Wherein a communication bus 1002 is used to enable connective communication between these components. The user interface 1003 may include a Display screen (Display), an input unit such as a Keyboard (Keyboard), and the optional user interface 1003 may also include a standard wired interface, a wireless interface. The network interface 1004 may optionally include a standard wired interface, a WIreless interface (e.g., a WIreless-FIdelity (WI-FI) interface). The Memory 1005 may be a Random Access Memory (RAM) Memory, or may be a Non-Volatile Memory (NVM), such as a disk Memory. The memory 1005 may alternatively be a storage device separate from the processor 1001.
Those skilled in the art will appreciate that the configuration shown in FIG. 1 does not constitute a limitation of the production apparatus and may include more or fewer components than shown, or some components may be combined, or a different arrangement of components.
As shown in fig. 1, a memory 1005, which is a storage medium, may include therein an operating system, a data storage module, a network communication module, a user interface module, and an electronic program.
In the production apparatus shown in fig. 1, the network interface 1004 is mainly used for data communication with a network server; the user interface 1003 is mainly used for data interaction with a user; the processor 1001 and the memory 1005 in the production equipment of the present invention may be provided in the production equipment, and the production equipment calls the unmanned aerial vehicle guided munition interchange design apparatus stored in the memory 1005 through the processor 1001 and executes the unmanned aerial vehicle guided munition interchange design method provided in the embodiment of the present application.
Referring to fig. 2, based on the hardware device of the foregoing embodiment, an embodiment of the present application provides an unmanned aerial vehicle guided weapon interchange design method, including:
step S10: acquiring the body parameters of a target unmanned aerial vehicle and the weapon parameters of a pre-equipped guidance weapon group; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons;
in the specific implementation process, the unmanned aerial vehicle for the actual combat assessment and identification test has the characteristics of large voyage, high altitude, subsonic velocity, capability of mounting guided weapons, large maneuverability and the like. Referring to test data that an unmanned aerial vehicle platform is only loaded with one guided weapon, the flight performance indexes of the unmanned aerial vehicle comprise: the maximum flat flying speed of the unmanned aerial vehicle is more than 0.7Ma, the practical lifting limit is more than 10000m, the voyage is more than 1000km, the normal overload is more than 8g, and the like.
The main indexes of the preassembled multi-type guided weapon include: the loading guided weapon has the weight of 10 kg-500 kg, the diameter of 100 mm-1000 mm of cylinder, the installation angle of 5-50 degrees, the working visual angle range of 20-360 degrees, the power consumption of 100 w-5000 w, the radio transmission rate of less than 18Mbps and the like.
The maximum weight of the multi-type guided weapon group is required to be less than or equal to the maximum weight loaded by the mission load of the unmanned aerial vehicle.
Specifically, the preassembled guidance weapon group comprises guidance weapons of various models, the guidance weapon group is placed in a load cabin of an unmanned aerial vehicle nose and is sequentially assembled at the same operation position of the unmanned aerial vehicle, but the guidance weapons of different models are different in weapon size, installation angle, communication interface quantity, communication interface type, power consumption requirement and the like, the unmanned aerial vehicle load cabin size, communication interface quantity, communication interface type, power supply capacity and the like cannot be matched with the guidance weapons of other models during exchange, the guidance weapons of different weights can cause the gravity center change of the unmanned aerial vehicle during exchange, and the airplane flight safety can be influenced by the change; therefore, various data of the unmanned aerial vehicle and the guided weapon need to be acquired for subsequent adjustment.
Step S20: according to the size relation between the maximum weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle, adjusting the loading space of the target unmanned aerial vehicle so as to enable the guided weapon to have a safe movement distance with the body shape of the target unmanned aerial vehicle when in operation;
in the specific implementation process, the multiple types of guided weapons are arranged in a load cabin of an unmanned aerial vehicle nose, the loading space is a cylinder, no other airborne equipment exists in the cabin, the maximum weapon size in the guided weapon group is used, 50-100 mm allowance is reserved for the length and the diameter of the size of the loading space of an unmanned aerial vehicle platform, the safe movement distance is reserved between the multiple types of guided weapons and the appearance of a machine body when the multiple types of guided weapons continuously rotate to work, interference is avoided, flight safety is influenced, meanwhile, the operation space for dismounting and mounting of the guided weapons is reserved, and the rapid operation of technicians is facilitated.
As an alternative embodiment, the step of adjusting the loading space of the target drone according to the size relationship between the largest weapon size in the guided weapon group and the size of the load compartment of the target drone, so that the guided weapon runs at a safe moving distance from the body shape of the target drone includes:
judging whether the maximum weapon size in the guided weapon group is larger than the load cabin size of the target unmanned aerial vehicle or not;
if yes, a partition plate is arranged in a front landing gear cabin of the target unmanned aerial vehicle.
In the concrete implementation process, some oversize guide weapons of size can surpass unmanned aerial vehicle load cabin, and the part of guide weapons can get into unmanned aerial vehicle's nose landing gear cabin, need set up the baffle in unmanned aerial vehicle's nose landing gear cabin, will surpass the part and separate with nose landing gear, takes place to interfere when avoiding the function, influences flight safety.
Step S30: adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
in the specific implementation process, the gravity center of the guided weapon with different weights can be changed before and after interchange and during the flight oil consumption process of the unmanned aerial vehicle. According to all parameters of the unmanned aerial vehicle and the guided weapon, the gravity center fluctuation range of the unmanned aerial vehicle is obtained and comprises a gravity center front limit, a design gravity center and a gravity center rear limit.
As an alternative embodiment, the step of adjusting the center of gravity of the target drone according to the weight of each guided weapon in the guided weapon group so that the center of gravity of the target drone does not exceed the fluctuation range of the center of gravity of the target drone includes:
adjusting the center of gravity of the target unmanned aerial vehicle by adjusting the position and/or the counterweight of the airborne equipment of the target unmanned aerial vehicle.
In the specific implementation process, after the guided weapons are exchanged, the gravity center of the unmanned aerial vehicle can be adjusted by adjusting the position of airborne equipment of the unmanned aerial vehicle, adjusting the balance weight and combining the airborne equipment and the balance weight, so that the gravity center fluctuation range is not beyond the preset gravity center fluctuation range.
Specifically, as shown in fig. 4, the gravity center fluctuation range of the unmanned aerial vehicle is: 7% mac before the focus, design focus 11% mac, 14% mac after the focus, unmanned aerial vehicle reloads behind first type guided weapon and the second type guided weapon of reloading, through the focus adjustment, design focus change is all around to focus between them to control is in focus fluctuation range, and unmanned aerial vehicle is in balanced state all the time, satisfies the guided weapon and exchanges the front and back, and unmanned aerial vehicle can the safe design requirement of flying.
Step S40: installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, wherein the mechanical interface is matched with the guided weapons of the plurality of models;
in the specific implementation process, the guided munitions are fixed on the structural frame of the unmanned aerial vehicle load compartment through some mechanical connections such as brackets and the like, but the difference of the sizes and the installation angles of the guided munitions of different models can cause that the mechanical connection between the unmanned aerial vehicle structural frame and the guided munitions needs to be readjusted when the munitions are interchanged. A fixed mechanical interface is designed on a structural frame of the unmanned aerial vehicle load cabin, so that the unmanned aerial vehicle load cabin is suitable for interchange of guided weapons with different lengths, diameters and installation angles.
As an alternative embodiment, the step of installing a mechanical interface on the target drone according to the installation angle of each guided weapon in the guided weapon group, the mechanical interface matching the plurality of models of guided weapons includes:
the mechanical interface is a metal support which can stretch out and draw back in length, zoom in and zoom out in diameter and rotate in angle according to the installation angles of different guided weapons.
In the specific implementation process, the mechanical interface is a metal support fixed on a load cabin of the unmanned aerial vehicle and comprises a circular ring and a Z-shaped rod, wherein the circular ring can be zoomed in and zoomed out in a variable diameter mode and can rotate around the spanwise diameter to adapt to different diameters and installation angles of the multi-type guided weapon; the Z-shaped rod can be extended or shortened according to different lengths of the multi-type guided weapons, the installation requirements of the guided weapons of different types can be met by adjusting the diameter and the angle of the circular ring in the metal support and the length of the Z-shaped rod, and the mechanical interface which is standardized and fixed on the structural frame can also meet the requirements of quick and efficient interchange.
Step S50: according to the number and the type of the communication interfaces of the guided weapon group, a standard communication interface is installed on the target unmanned aerial vehicle;
in the specific implementation process, an airborne equipment flight control computer of the unmanned aerial vehicle receives data signals from the guided weapons, and increases corresponding types and numbers of communication interfaces special for data transmission of the guided weapons according to the number of the communication interfaces of the guided weapons with the largest number and all types of the communication interfaces of the guided weapons to be assembled, so that the data transmission requirements of control, recording, detection and the like of the guided weapons are met, and the problems of insufficient number of the communication interfaces or unmatched types can not occur after interchange.
Step S60: and changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guided weapon group.
In the specific implementation process, the full-electromechanical power consumption of the unmanned aerial vehicle mainly comprises two parts of power consumption of an unmanned aerial vehicle platform and power consumption of a task load, and an electrical system needs to be designed and changed in order to meet normal work before and after the exchange of a guided weapon.
As an optional implementation mode, the power supply modes of the guided weapon group comprise a plurality of direct current power supply modes;
the step of changing the target unmanned aerial vehicle electrical system according to the power consumption requirement of the guided weapon group comprises:
and according to the direct current power supply mode of the guided weapon group, setting different direct current power supply devices and direct current conversion units on the target unmanned aerial vehicle.
In the specific implementation process, the input voltage of the multi-type guided weapon is supplied by two different direct currents, and the unmanned aerial vehicle is supplied by one direct current. Divide into two the tunnel with the direct current through distribution equipment, carry out DC supply for unmanned aerial vehicle and the guidance weapon the same with unmanned aerial vehicle power supply mode all the way, another way carries out DC supply for the guidance weapon different with unmanned aerial vehicle power supply mode to carry out the vary voltage through joining in marriage the dress DC conversion unit with different direct currents and handle, in order to satisfy the power consumption requirement of the guidance weapon of different models after exchanging.
As an alternative embodiment, the step of modifying the target drone electrical system according to the power demand of the guided weapon group includes:
through reducing target unmanned aerial vehicle's power consumption, satisfy the maximum power consumption demand of guide wu jia group.
In the specific implementation process, according to the characteristics of actual combat test tasks, the electric power consumption that the unmanned aerial vehicle platform does not use or use less needs to be reduced in a refined mode, the electricity utilization ratio of the whole machine is improved to the maximum extent, the low-cost design that the storage battery is not increased and the maximum electric power consumption of the guided weapons can be guaranteed is realized, meanwhile, the use requirements of the guided weapons with other different powers can be met, and electric power support is provided for the rapid exchange of multiple guided weapons.
Specifically, W-J is A and A is more than or equal to A ', wherein, the total rated capacity of unmanned aerial vehicle electrical system is W, the biggest power consumption demand of many types of guidance weapon is A', the power consumption that the unmanned aerial vehicle platform can reduce is J, the power consumption that is used for the mission load is A.
As an alternative embodiment, the step of modifying the target drone electrical system according to the power demand of the guided weapon group includes:
and meeting the single limit power utilization requirement of the guided weapon by overloading the engine of the target unmanned aerial vehicle and limiting the single power utilization time.
In practice, actual combat trials often involve a single, single-inventory, special mission that requires the drone to provide a short period of extreme power to support the guided munitions to complete the mission.
Specifically, the power utilization requirement of the single catalogue limit power of the guided weapon is met by overloading the rotating speed of the unmanned aerial vehicle engine by 106-125% and limiting the single power utilization time to be less than or equal to 2min, so that the completion of special tasks is guaranteed.
The unmanned aerial vehicle platform is adjusted according to the design method, loading of a plurality of guided weapons can be completed in one unmanned aerial vehicle flight operation in an actual combat test, and rapid exchange of the guided weapons is realized.
Through the above description, it is not difficult to discover that the design such as loading space adjustment, weight focus match, take universalization interface, change onboard system is carried out to unmanned aerial vehicle to this embodiment, can load the guidance weapon of multiple different models in proper order in the same operation position of same unmanned aerial vehicle platform, and efficiency is higher in the actual combat experiment.
Referring to fig. 3, based on the same inventive concept, an embodiment of the present application further provides an unmanned aerial vehicle guided weapon interchange design device, including:
the data acquisition module is used for acquiring the fuselage parameters of the target unmanned aerial vehicle and the weapon parameters of the pre-equipped guided weapon group; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons;
the loading space adjusting module is used for adjusting the loading space of the target unmanned aerial vehicle according to the size relation between the size of the largest weapon in the guided weapon group and the size of a load cabin of the target unmanned aerial vehicle, so that a safe movement distance is reserved between the guided weapon and the body shape of the target unmanned aerial vehicle when the guided weapon operates;
the gravity center adjusting module is used for adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
the mechanical interface installation module is used for installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, and the mechanical interface is matched with the guided weapons of multiple models;
the communication interface installation module is used for installing a standardized communication interface on the target unmanned aerial vehicle according to the number and the type of the communication interfaces of the guided weapon group;
and the electrical system changing module is used for changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guidance weapon group.
It should be noted that, in the present embodiment, each module in the device for designing and exchanging an unmanned aerial vehicle guided weapon corresponds to each step in the method for designing and exchanging an unmanned aerial vehicle guided weapon in the foregoing embodiment one by one, and therefore, the specific implementation of the present embodiment may refer to the implementation of the method for designing and exchanging an unmanned aerial vehicle guided weapon, and is not described herein again.
Furthermore, in an embodiment, an embodiment of the present application further provides a production apparatus, which includes a processor, a memory, and a computer program stored in the memory, and when the computer program is executed by the processor, the steps of the method in the foregoing embodiment are implemented.
Furthermore, in an embodiment, an embodiment of the present application further provides a computer storage medium having a computer program stored thereon, where the computer program is executed by a processor to implement the steps of the method in the foregoing embodiments.
In some embodiments, the computer-readable storage medium may be memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash, magnetic surface memory, optical disk, or CD-ROM; or may be various devices including one or any combination of the above memories. The computer may be a variety of computing devices including intelligent terminals and servers.
In some embodiments, executable instructions may be written in any form of programming language (including compiled or interpreted languages), in the form of programs, software modules, scripts or code, and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.
By way of example, executable instructions may correspond, but do not necessarily have to correspond, to files in a file system, and may be stored in a portion of a file that holds other programs or data, such as in one or more scripts in a hypertext Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code).
By way of example, executable instructions may be deployed to be executed on one computing device or on multiple computing devices at one site or distributed across multiple sites and interconnected by a communication network.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or system that comprises the element.
The above-mentioned serial numbers of the embodiments of the present application are merely for description and do not represent the merits of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solution of the present application or portions thereof contributing to the prior art may be substantially embodied in the form of a software product, the computer software product being stored in a storage medium (e.g. a rom/ram, a magnetic disk, an optical disk) and including instructions for enabling a multimedia terminal (e.g. a mobile phone, a computer, a television receiver, or a network device) to execute the method according to the embodiments of the present application
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all modifications of equivalent structures and equivalent processes, which are made by the contents of the specification and the drawings of the present application, or which are directly or indirectly applied to other related technical fields, are included in the scope of the present application.
Claims (11)
1. An unmanned aerial vehicle guided weapon interchange design method is characterized by comprising the following steps:
acquiring the body parameters of a target unmanned aerial vehicle and the weapon parameters of a pre-equipped guidance weapon group; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons;
according to the size relation between the maximum weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle, adjusting the loading space of the target unmanned aerial vehicle so as to enable the guided weapon to have a safe movement distance with the body shape of the target unmanned aerial vehicle when in operation;
adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, wherein the mechanical interface is matched with the guided weapons of the plurality of models;
according to the number and the type of the communication interfaces of the guided weapon group, a standard communication interface is installed on the target unmanned aerial vehicle;
and changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guided weapon group.
2. The unmanned aerial vehicle guided munition interchange design method as defined in claim 1, wherein the step of adjusting the loading space of the target unmanned aerial vehicle according to the magnitude relationship between the largest weapon size in the guided weapon group and the size of the load compartment of the target unmanned aerial vehicle so that the guided weapon operates with a safe movement distance from the body shape of the target unmanned aerial vehicle comprises:
judging whether the maximum weapon size in the guided weapon group is larger than the load cabin size of the target unmanned aerial vehicle or not;
if yes, a partition plate is arranged in a front landing gear cabin of the target unmanned aerial vehicle.
3. The unmanned aerial vehicle guided munition interchange design method as claimed in claim 1, wherein the step of adjusting the center of gravity of the target unmanned aerial vehicle according to the weight of each guided munition in the guided munition bank so that the center of gravity of the target unmanned aerial vehicle does not exceed the fluctuation range of the center of gravity of the target unmanned aerial vehicle comprises:
adjusting the center of gravity of the target unmanned aerial vehicle by adjusting the position and/or the counterweight of the airborne equipment of the target unmanned aerial vehicle.
4. The unmanned aerial vehicle guided munition interchange design method of claim 1, wherein said step of installing a mechanical interface on the target unmanned aerial vehicle according to an installation angle of each guided munition in the set of guided munitions, the mechanical interface matching the plurality of models of guided munitions comprises:
the mechanical interface is a metal support which can stretch out and draw back in length, zoom in and zoom out in diameter and rotate in angle according to the installation angles of different guided weapons.
5. The unmanned aerial vehicle guided munition interchange design method of claim 1, wherein the power supply mode of the guided munition set comprises a plurality of direct current power supply modes;
the step of changing the target unmanned aerial vehicle electrical system according to the power consumption requirement of the guided weapon group comprises:
and according to the direct current power supply mode of the guided weapon group, setting different direct current power supply devices and direct current conversion units on the target unmanned aerial vehicle.
6. The unmanned aerial vehicle guided munition interchange design method of claim 5, wherein the step of modifying the target unmanned aerial vehicle electrical system based on power requirements of the guided munition pack comprises:
through reducing target unmanned aerial vehicle's power consumption, satisfy the maximum power consumption demand of guide wu jia group.
7. The unmanned aerial vehicle guided munition interchange design method of claim 6, wherein the step of modifying the target unmanned aerial vehicle electrical system based on power requirements of the guided munition pack comprises:
and meeting the single limit power utilization requirement of the guided weapon by overloading the engine of the target unmanned aerial vehicle and limiting the single power utilization time.
8. The unmanned aerial vehicle guided munition interchange design method as defined in claim 1, wherein the step of modifying the target unmanned aerial vehicle electrical system based on power requirements of the guided munition pack further comprises:
and adjusting the target unmanned aerial vehicle according to the unmanned aerial vehicle guided weapon interchange design method.
9. An unmanned aerial vehicle guided munition interchange design device, comprising:
the data acquisition module is used for acquiring the fuselage parameters of the target unmanned aerial vehicle and the weapon parameters of the pre-equipped guided weapon group; the fuselage parameters comprise the size of a load compartment, the fluctuation range of the gravity center, the operation position of a guided weapon and the power supply capacity, the weapon parameters comprise the weapon size, the total weight, the installation angle, the number of communication interfaces, the type of the communication interfaces and the power consumption requirement, and the guided weapon group comprises a plurality of types of guided weapons;
the loading space adjusting module is used for adjusting the loading space of the target unmanned aerial vehicle according to the size relation between the size of the largest weapon in the guided weapon group and the size of a load cabin of the target unmanned aerial vehicle, so that a safe movement distance is reserved between the guided weapon and the body shape of the target unmanned aerial vehicle when the guided weapon operates;
the gravity center adjusting module is used for adjusting the gravity center of the target unmanned aerial vehicle according to the weight of each guided weapon in the guided weapon group, so that the gravity center of the target unmanned aerial vehicle does not exceed the gravity center fluctuation range of the target unmanned aerial vehicle;
the mechanical interface installation module is used for installing a mechanical interface on the target unmanned aerial vehicle according to the installation angle of each guided weapon in the guided weapon group, and the mechanical interface is matched with the guided weapons of the plurality of models;
the communication interface installation module is used for installing a standardized communication interface on the target unmanned aerial vehicle according to the number and the type of the communication interfaces of the guided weapon group;
and the electrical system changing module is used for changing the target unmanned aerial vehicle electrical system according to the power utilization requirement of the guidance weapon group.
10. A production device, characterized in that it comprises a memory in which a computer program is stored and a processor which executes said computer program implementing the method according to any one of claims 1-7.
11. A computer-readable storage medium, having a computer program stored thereon, which, when executed by a processor, performs the method of any one of claims 1-7.
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